Curved seal for adjacent gas turbine components

ABSTRACT

A flexible seal for sealing between two adjacent gas turbine components includes a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially offset from the forward end. In other cases, the forward and aft ends are axially, radially, and circumferentially offset from one another. A method of sealing using the flexible seal includes inserting, in an axial direction, the aft end of the flexible seal into a recess defined by respective seal slots of two adjacent gas turbine components; and pushing the flexible seal in an axial direction through the recess until the forward end is disposed within the recess.

PRIORITY CLAIM

This application is a continuation of prior pending U.S. patentapplication Ser. No. 16/012,380, filed Jun. 19, 2018, which isincorporated by reference herein in its entirety.

STATEMENT REGARDING GOVERNMENT FUNDING

The subject matter of this disclosure was made with support from theUnited States government, under Contract Number DE-FE0023965, which wasawarded by the U.S. Department of Energy. The government has certainrights in this invention.

TECHNICAL FIELD

The present disclosure relates generally to the field of gas turbinesand, more particularly, to seals for integrated combustor nozzles thatdefine separate combustion zones within an annular combustor and thataccelerate the flow entering the turbine section. The continuouslycurved seals are configured to seal the inner and outer liner segmentsto facilitate installation and removal of both the seals and theintegrated combustor nozzles from the annular combustor.

BACKGROUND

Some conventional turbo machines, such as gas turbine systems, areutilized to generate electrical power. In general, gas turbine systemsinclude a compressor, one or more combustors, and a turbine. Air may bedrawn into a compressor, via its inlet, where the air is compressed bypassing through multiple stages of rotating blades and stationarynozzles. The compressed air is directed to the one or more combustors,where fuel is introduced, and a fuel/air mixture is ignited and burnedto form combustion products. The combustion products function as theoperational fluid of the turbine.

The operational fluid then flows through a fluid flow path in a turbine,the flow path being defined between a plurality of rotating blades and aplurality of stationary nozzles disposed between the rotating blades,such that each set of rotating blades and each corresponding set ofstationary nozzles defines a turbine stage. As the plurality of rotatingblades rotate the rotor of the gas turbine system, a generator, coupledto the rotor, may generate power from the rotation of the rotor. Therotation of the turbine blades also causes rotation of the compressorblades, which are coupled to the rotor.

In recent years, efforts have been made to design can-annular combustionsystems in which the first stage of turbine nozzles is integrated withthe aft ends of the combustion cans. Such efforts have resulted in aso-called “transition nozzle” that accelerates and turns the flow as itenters the turbine section.

More recently, development efforts have applied the transition nozzletechnology in an annular combustion system, leading to the creation of asegmented annular combustion system, as described in commonly assignedU.S. Patent Application Publication No. 2017-027639. In a segmentedannular combustion system, the inner liner shell and the outer linershell are segmented circumferentially into individual modules, and anarray of fuel injection panels extends between the inner liner shellsegments and the outer liner shell segments of the annular combustor tocreate a set of units called “integrated combustor nozzles.” A pluralityof combustion zones is defined between adjacent pairs of integratedcombustor nozzles within the annular combustor. The integrated combustornozzles are shaped like airfoils without a leading edge, and thetrailing edge (aft end) of each integrated combustor nozzle defines aturbine nozzle capable of turning and accelerating the flow ofcombustion gases into the turbine.

To optimize the performance of such a combustion system, it is necessaryto seal between adjacent integrated combustor nozzles along the innerliner shell segment and the outer liner shell segment. Initial effortsto seal these components relied upon multiple straight seals that wereinstalled circumferentially into seal slots along the circumferentialedges of the liner shell segments. This installation method proveddifficult, especially with small seal components, both in maintainingthe position of the seal during installation of the subsequentintegrated combustor nozzle and in preventing the seal from beingcrushed (or otherwise damaged) when the subsequent integrated combustornozzle was installed. Moreover, if one of the seals slipped out ofposition during installation, the technician was faced with thedifficult task of its retrieval from within the turbine.

Another issue with the prior sealing efforts is that, as the seals areinstalled end-to-end over the axial length of the integrated combustornozzle, leakages arise between the axial segments of the seal. Suchleakages reduce the amount of air flow usable for other purposes, suchas cooling or combustion.

Finally, the dogleg shape of the integrated combustor nozzles and theprior sealing efforts made removal of a single integrated combustornozzle difficult. Because multiple seals were installed end-to-end alongthe axial length of the integrated combustor nozzle, it was impossibleto remove the seals axially. As a result, the integrated combustornozzles had to be “fanned out” by forcibly shifting the integratedcombustor nozzles in a circumferential direction, and the integratedcombustor nozzle to be removed had to be wrestled out of its nestedposition within the array of integrated combustor nozzles.

SUMMARY

A flexible seal for sealing between two adjacent gas turbine componentsincludes a forward end, an aft end axially separated from the forwardend, and an intermediate portion between the forward end and the aftend. The intermediate portion defines a continuous curve in thecircumferential direction, such that the aft end is circumferentiallyoffset from the forward end. In other cases, the forward and aft endsare axially, radially, and circumferentially offset from one another. Amethod of sealing using the flexible seal includes inserting, in anaxial direction, the aft end of the flexible seal into a recess definedby respective seal slots of two adjacent gas turbine components; andpushing the flexible seal in an axial direction through the recess untilthe forward end is disposed within the recess.

Specifically, according to one aspect of the present disclosure, aflexible seal for sealing between two adjacent gas turbine components isprovided. The flexible seal includes a forward end, an aft end axiallyseparated from the forward end, and an intermediate portion between theforward end and the aft end. The intermediate portion defines acontinuous curve in the circumferential direction, such that the aft endis circumferentially offset from the forward end.

According to another aspect of the present disclosure, a flexible sealfor sealing between two adjacent gas turbine components is provided. Theflexible seal includes a seal body having a forward end and an aft end,wherein the aft end is axially, radially, and circumferentially offsetfrom the forward end.

According to yet another aspect of the present disclosure, a method ofsealing between two adjacent gas turbine components using a seal havinga first end and an opposing second end is provided. The method includes:inserting, in an axial direction, the second end of the flexible sealinto a recess defined by respective seal slots in each continuouslycurved circumferential sealing surface of the two adjacent gas turbinecomponents, wherein the first end is axially, radially, andcircumferentially offset from the second end; and pushing the flexibleseal in an axial direction through the recess until the first end isdisposed within the recess.

BRIEF DESCRIPTION OF THE DRAWINGS

The specification, directed to one of ordinary skill in the art, setsforth a full and enabling disclosure of the present system and method,including the best mode of using the same. The specification refers tothe appended figures, in which:

FIG. 1 is a functional block diagram of an exemplary gas turbine thatmay incorporate various embodiments of the present disclosure;

FIG. 2 is an upstream view of an exemplary segmented annular combustor,which may be used as the combustion section of the gas turbine of FIG.1, according to at least one embodiment of the present disclosure;

FIG. 3 is a downstream perspective view of three circumferentiallyadjacent integrated combustor nozzles (of the segmented annularcombustor of FIG. 2) to which three fuel injection modules are mounted,according to a conventional design;

FIG. 4 is an overhead perspective view of two circumferentially adjacentintegrated combustor nozzles, including a first call-out bubbleillustrating a forward end of a seal and a second call-out bubbleillustrating a seal recess, according to the present disclosure;

FIG. 5 is a schematic illustration of a seal of a uniform width disposedin a recess of non-uniform width, including a first call-outillustrating a symmetrical seal recess and a second call-outillustrating an asymmetrical seal recess, according to one aspect of thepresent disclosure;

FIG. 6 is a schematic illustration of a seal of non-uniform widthdisposed in a recess of uniform width, including a first call-outillustrating a portion of the seal having a first width and a secondcall-out illustrating a portion of the seal having a second widthdifferent from the first width, according to another aspect of thepresent disclosure;

FIG. 7 is a side perspective view of one of the integrated combustornozzles of FIG. 4, including a first call-out bubble illustrating an aftend slot for the inner liner seal and a second call-out bubbleillustrating an aft end slot for the outer liner seal, according to thepresent disclosure;

FIG. 8 is a side perspective view of an outer liner seal, as may be usedwith the present integrated combustor nozzles;

FIG. 9 is an overhead plan view of the outer liner seal of FIG. 8;

FIG. 10 is a side perspective view of an inner liner seal, as may beused with the present integrated combustor nozzles;

FIG. 11 is a schematic side view of an aft end of the outer liner sealof FIG. 8, illustrating a multi-ply seal;

FIG. 12 is a schematic perspective view of an anchor attached to aforward end of the outer liner seal of FIG. 8, in which the anchordefines a through-hole for removal of the outer liner seal;

FIG. 13 is a schematic perspective view of an anchor attached to aforward end of the outer liner seal of FIG. 8, in which the anchordefines an indentation from an upper surface of the anchor for removalof the outer liner seal;

FIG. 14 is a schematic perspective view of an anchor attached to aforward end of the outer liner seal of FIG. 8, in which the anchordefines an indentation from a bottom surface of the anchor for removalof the outer liner seal;

FIG. 15 is a schematic perspective view of a forward end of the outerliner seal of FIG. 8 installed within an anchor, according to an aspectof the present disclosure;

FIG. 16 is a schematic cross-sectional side view of the outer liner sealand the anchor of FIG. 15; and

FIG. 17 is a schematic cross-sectional side view of the outer liner sealand the anchor of FIG. 15, as installed within a forward end of a sealslot, according to another aspect of the present disclosure;

FIG. 18 is a perspective, forward-looking-aft view of threecircumferentially adjacent integrated combustor nozzles, one of which ispartially removed;

FIG. 19 is a perspective, inward-looking-outward view of the integratedcombustor nozzles of FIG. 18, as shown from the inner liner segments,with one of the integrated combustor nozzles being further removed;

FIG. 20 is a perspective, aft-looking-forward view of the integratedcombustor nozzles of FIG. 18, as shown from the aft end of theintegrated combustor nozzles; and

FIG. 21 is a perspective, forward-looking-aft view of the integratedcombustor nozzles of FIG. 18, in which one of the integrated combustornozzles is fully removed.

DETAILED DESCRIPTION

Reference will now be made in detail to various embodiments of thepresent disclosure, one or more examples of which are illustrated in theaccompanying drawings. The detailed description uses numerical andletter designations to refer to features in the drawings. Like orsimilar designations in the drawings and description have been used torefer to like or similar parts of the disclosure.

To clearly describe the current integrated combustor nozzle, certainterminology will be used to refer to and describe relevant machinecomponents within the scope of this disclosure.

To the extent possible, common industry terminology will be used andemployed in a manner consistent with the accepted meaning of the terms.Unless otherwise stated, such terminology should be given a broadinterpretation consistent with the context of the present applicationand the scope of the appended claims. Those of ordinary skill in the artwill appreciate that often a particular component may be referred tousing several different or overlapping terms. What may be describedherein as being a single part may include and be referenced in anothercontext as consisting of multiple components. Alternatively, what may bedescribed herein as including multiple components may be referred toelsewhere as a single integrated part.

In addition, several descriptive terms may be used regularly herein, asdescribed below. The terms “first”, “second”, and “third” may be usedinterchangeably to distinguish one component from another and are notintended to signify location or importance of the individual components.

As used herein, “downstream” and “upstream” are terms that indicate adirection relative to the flow of a fluid, such as the working fluidthrough the turbine engine. The term “downstream” corresponds to thedirection of flow of the fluid, and the term “upstream” refers to thedirection opposite to the flow (i.e., the direction from which the fluidflows). The terms “forward” and “aft,” without any further specificity,refer to relative position, with “forward” being used to describecomponents or surfaces located toward the front (or compressor) end ofthe engine or toward the inlet end of the combustor, and “aft” beingused to describe components located toward the rearward (or turbine) endof the engine or toward the outlet end of the combustor. The term“inner” is used to describe components in proximity to the turbineshaft, while the term “outer” is used to describe components distal tothe turbine shaft.

It is often required to describe parts that are at differing radial,axial and/or circumferential positions. As shown in FIG. 1, the “A” axisrepresents an axial orientation. As used herein, the terms “axial”and/or “axially” refer to the relative position/direction of objectsalong axis A, which is substantially parallel with the axis of rotationof the gas turbine system. As further used herein, the terms “radial”and/or “radially” refer to the relative position or direction of objectsalong an axis “R”, which intersects axis A at only one location. In someembodiments, axis R is substantially perpendicular to axis A. Finally,the term “circumferential” refers to movement or position around axis A(e.g., axis “C”). The term “circumferential” may refer to a dimensionextending around a center of a respective object (e.g., a rotor).

The terminology used herein is for the purpose of describing particularembodiments only and is not intended to be limiting. As used herein, thesingular forms “a”, “an” and “the” are intended to include the pluralforms as well, unless the context clearly indicates otherwise. It willbe further understood that the terms “comprises” and/or “comprising,”when used in this specification, specify the presence of statedfeatures, integers, steps, operations, elements, and/or components, butdo not preclude the presence or addition of one or more other features,integers, steps, operations, elements, components, and/or groupsthereof.

Each example is provided by way of explanation, not limitation. In fact,it will be apparent to those skilled in the art that modifications andvariations can be made without departing from the scope or spiritthereof. For instance, features illustrated or described as part of oneembodiment may be used on another embodiment to yield a still furtherembodiment. Thus, it is intended that the present disclosure covers suchmodifications and variations as come within the scope of the appendedclaims and their equivalents.

Although exemplary embodiments of the present disclosure will bedescribed generally in the context of a segmented annular combustionsystem for a land-based power-generating gas turbine for purposes ofillustration, one of ordinary skill in the art will readily appreciatethat embodiments of the present disclosure may be applied to any type ofcombustor for a turbomachine and are not limited to annular combustionsystems for land-based power-generating gas turbines unless specificallyrecited in the claims.

Referring now to the drawings, FIG. 1 schematically illustrates anexemplary gas turbine 10. The gas turbine 10 generally includes an inletsection 12, a compressor 14 disposed downstream of the inlet section 12,a combustion section 16 disposed downstream of the compressor 14, aturbine 18 disposed downstream of the combustion section 16, and anexhaust section 20 disposed downstream of the turbine 18. Additionally,the gas turbine 10 may include one or more shafts 22 (also known as“rotors”) that couple the compressor 14 to the turbine 18.

During operation, air 24 flows through the inlet section 12 and into thecompressor 14, where the air 24 is progressively compressed, thusproviding compressed air 26 to the combustion section 16. At least aportion of the compressed air 26 is mixed with a fuel 28 within thecombustion section 16 and burned to produce combustion gases 30. Thecombustion gases 30 flow from the combustion section 16 to into theturbine 18, where thermal and/or kinetic energy are transferred from thecombustion gases 30 to rotor blades (not shown) attached to the shaft22, thereby causing the shaft 22 to rotate. The mechanical rotationalenergy may then be used for various purposes, such as to power thecompressor 14 and/or to generate electricity, via a generator 21 coupledto the shaft 22. The combustion gases 30 exiting the turbine 18 may thenbe exhausted from the gas turbine 10, via the exhaust section 20.

FIG. 2 provides an upstream (i.e., an aft-looking-forward) view of thecombustion section 16, according to various embodiments of the presentdisclosure. As shown in FIG. 2, the combustion section 16 may be anannular combustion system and, more specifically, a segmented annularcombustor 36 in which an array of integrated combustor nozzles 100 arearranged circumferentially about an axial centerline 38 of the gasturbine 10. The axial centerline 38 may be coincident with the gasturbine shaft 22. The segmented annular combustion system 36 may be atleast partially surrounded by an outer casing 32, sometimes referred toas a compressor discharge casing. The compressor discharge casing 32,which receives compressed air 26 from the compressor 14 (FIG. 1), may atleast partially define a high-pressure air plenum 34 that at leastpartially surrounds various components of the combustor 36. Thecompressed air 26 is used for combustion, as described above, and forcooling combustor hardware.

The segmented annular combustor 36 includes a circumferential array ofintegrated combustor nozzles 100. Each integrated combustor nozzle 100includes an inner liner segment 106, an outer liner segment 108 radiallyseparated from the inner liner segment 106, and a hollow or semi-hollowpanel 110 extending radially between the inner liner segment 106 and theouter liner segment 108, thus generally defining an “I”-shaped assembly.The panels 110 separate the combustion chamber into an annular array offluidly separated combustion zones.

At the upstream end of the segmented annular combustor 36, a fuelinjection module 300 extends circumferentially between each pair of thepanels 110 and radially between the inner liner segment 106 and theouter liner segment 108. The fuel injection modules 300 introduce afuel/air mixture into the combustion zones from a burner, a swirlingfuel nozzle (swozzle), or a bundled tube fuel nozzle (e.g., as shown inFIG. 3). Each fuel injection module 300 has at least one fuel conduitsupplying the fuel injection modules 300, which, for illustrativepurposes, is represented by a circle. If desired for greater operationalrange (e.g., turn-down) and lower emissions, the panels 110 may alsointroduce fuel in one or more stages downstream of the combustion zonescreated by the injection of the fuel/air mixtures delivered by the fuelinjection modules 300.

FIG. 3 illustrates a set of three respective integrated combustornozzles 1000, which are assembled with three exemplary fuel injectionmodules 1300, according to conventional practice (for example, asdescribed in commonly assigned U.S. Patent Application Publication No.2017-027639). Each integrated combustor nozzle 1000 includes an innerliner segment 1106, an outer liner segment 1108, and a hollow orsemi-hollow fuel injection panel 1110 that extends between the innerliner segment 1106 and the outer liner segment 1108. Each fuel injectionpanel 1110 includes a forward portion 1112 and an aft portion 1114. Theaft portion 1114 defines the shape of a first-stage turbine nozzle in aconventional gas turbine. The forward portion 1112 and the aft portion1114 are connected by a pair of side walls (one of which is shown as asuction-side wall 1118).

When all the integrated combustor nozzles 1000 are installed, therespective inner liner segments 1106 define an inner boundary of thecombustion chamber, and the respective outer liner segments 1108 definedan outer boundary of the combustion chamber (as shown in FIG. 2).

In the exemplary embodiment shown in FIG. 3, the outer liner segments1108 may be provided with impingement cooling panels 1178, which areradially spaced from the outer liner segments 1108 and which include aplurality of impingement holes 1182 that are in fluid communication withthe gap between the outer liner segments 1108 and the respectiveimpingement cooling panels 1178. The inner liner segments 1106 may besimilarly cooled.

The segmented annular combustion system 1036 further includes aplurality of annularly arranged fuel injection modules 1300, each ofwhich may extend circumferentially between two circumferentiallyadjacent fuel injection panels 1100 and/or at least partially radiallybetween a respective inner liner segment 1106 and outer liner segment1108. The fuel injection module 1300 may include a bundled tube fuelnozzle that includes a plurality of premixing tubes 1322 extendingthrough one or more fuel plenums (not shown) defined between axiallyseparated plates 1316, 1360. In the exemplary configuration of theconventional design, the plurality of premixing tubes 1322 of the fuelinjection module 1300 may be arranged into a first subset of tubes 1356and a second subset of tubes 1358. Fuel to the first subsets of tubes1356 and the second subset of tubes 1358 may be supplied via fuelconduits 1382 and/or 1392.

Other arrangements may, of course, be used. Indeed, the bundled tubefuel nozzles may be replaced by any type of fuel nozzle or burner (suchas a swirling fuel nozzle or swozzle).

The fuel injection panel 1110, which extends radially between the innerliner segment 1106 and the outer liner segment 1108, has a shape thatcurves in the circumferential direction from the forward end 1112 to theaft end 1114 to turn and accelerate the flow of combustion products 30into the turbine section 18. Additionally, the fuel injection panel 1110may include a difference in height in the radial direction, such thatthe forward end 1112 of the fuel injection panel 1110 has a greaterheight than the aft end 1114.

The inner and outer liner segments 1106, 1108 in the conventional designare configured with a dogleg shape to generally reflect the curved shapeof the fuel injection panel 1110, and the adjacent sealing surfaces(e.g., 1122 a, 1122 b) of each liner segment 1106, 1108 are disposed atan oblique angle relative to one another. Such a configuration makessealing along the joints 1122 between adjacent inner liner segments 1106and between adjacent outer liner segments 1108 challenging.

In the conventional configuration shown in FIG. 3, the sealing surfaces1122 a, 1122 b are provided with a C-shaped slot, or open channel,extending substantially along the length of the sealing surfaces 1122 a,1122 b, and within which multiple straight seal components (not shown)are installed end-to-end to seal the joint 1122 between adjacent linersegments 1106 and/or 1108. The use of multiple seals is known to causegreater leakage, for example, between seal components, as compared to asingle component seal.

Moreover, in the conventional configuration, it is necessary to installthe seal components (not shown) individually, as each integratedcombustor nozzle 1000 is installed into the gas turbine 10. Thus, afteran integrated combustor nozzle 1000 is positioned, the respective (twoor more) seal components are inserted in a circumferential (sideways)direction into the C-shaped slots defined along the sealing surfaces1122 a, 1122 b of a first integrated combustor nozzle 1000, and then acircumferentially adjacent integrated combustor nozzle 1000 ismaneuvered into position. Maintaining the multiple seals in theirrespective positions within the slots and preventing the seals fromfalling out of the respective slots while installing the subsequentintegrated combustor nozzle 1000 is difficult, and care must be taken toinstall the subsequent integrated combustor nozzle 1000 in a manner thatprevents the seal components from being crushed or damaged.

Additionally, the dogleg shape of the integrated combustor nozzle 1000and the use of multiple end-to-end seals makes removal of any givenintegrated combustor nozzle 1000 difficult to achieve. Such removalrequired removing the seals at the forward (inlet) ends of the givenintegrated combustor nozzle 1000 and several adjacent integratedcombustor nozzles 1000, “fanning out” the adjacent integrated combustornozzles by pushing their forward ends circumferentially away from thegiven integrated combustor nozzle 1000, and then wresting the givenintegrated combustor nozzle 1000 from its position within the array. Theremoval process could also lead to damage of the aft seals, as theintegrated combustor nozzles 1000 are repositioned.

These problems are addressed by the present integrated combustor nozzle100 and its continuous seals 140 and 160, as shown in FIGS. 4 through21.

FIG. 4 illustrates a pair of circumferentially adjacent integratedcombustor nozzles 100, as shown from a forward end 112. Each integratedcombustor nozzle 100 includes an inner liner segment 106, an outer linersegment 108 radially separated from the inner liner segment 106, and afuel injection panel 110 extending radially between the inner linersegment 106 and the outer liner segment 108. The fuel injection panel110 includes a first (pressure) side wall 116 and a second (suction)side wall 118 that intersect at an aft end 114 to define a turbine(stage one) nozzle. For the sake of clarity, the fuel injection modules(as described above) are not shown, but should be understood as beingpositioned between the fuel injection panels 110 at the forward ends 112of the integrated combustor nozzles 100.

The inner liner segment 106 includes a first sealing surface 130 and asecond sealing surface 134, both of which extend in an axial directionand curve continuously in a circumferential direction from the forwardend 112 to the aft end 114 (shown in FIG. 7). In one embodiment, thesealing surfaces 130, 134 may also curve in a radial direction,optionally with one or more inflection points.

Likewise, the outer liner segment 108 includes a first sealing surface150 and a second sealing surface 154, both of which extend in an axialdirection and curve continuously in a circumferential direction from theforward end 112 to an aft end 114. In one embodiment, the sealingsurfaces 150, 154 may also curve in a radial direction, optionally withone or more inflection points.

To facilitate installation and removal of the integrated combustornozzles 100 and their respective seals 140, 160, the inner and outerliner segments 106, 108 are provided with a curved shape along theirrespective sealing surfaces 130, 134, 150, 154, according to thefollowing parameters. As described above, a first parameter is that thecurved shape is continuous in the circumferential direction. In someinstances, the curved shaped may be “monotonic” in the circumferentialdirection, meaning that, moving from the forward end to the aft end ofthe sealing surfaces 130, 134, 150, 154, the curve has a constant radiusand has no inflection points where the radius of the curve changes(increases or decreases) to cause a change in the concavity of thecurve. (It should be noted that the sealing surfaces 130, 134, 150, 154may include one or more inflection points only in the radial direction,as descried below.) In some instances, the curved shape may have acontinuously decreasing radius from the forward end 112 to the aft end114, such as may be defined by a parabola or ellipse.

A second parameter is that the curved shape cannot intersect any part ofthe fuel injection panel 110, including the aft end 114. Because thefuel injection panel 110 is a discrete unit designed with fuel deliverypassages to deliver fuel to the downstream combustion zones and separateair passages to ensure adequate cooling of the fuel injection panel 110,disrupting the flow of fluids through the fuel injection panel 110 isundesirable and would further complicate the sealing of adjacentintegrated combustor nozzles 100.

A third parameter is that the same curved profile is used for the innerliner segment 106 and the outer liner segment 108. Said differently, thecurved profile is translated radially through both the both inner linersegment 106 and the outer liner segment 108. Such a configurationpermits the installation and removal of individual integrated combustornozzles 100 in a generally axial direction, pushing or pulling theintegrated combustor nozzles 100 along the curve and into or out ofposition (as shown in FIGS. 18 through 21).

Yet another parameter is that all the integrated combustor nozzles 100are identical in the curved profile of the sealing surfaces 130, 134,150, 154 of the inner liner segments 106 and the outer liner segments108. There is no “key” integrated combustor nozzle 100 that is slightlydifferent from the other integrated combustor nozzles 100 to secure theposition of the annular array of integrated combustor nozzles 100.Rather, because each integrated combustor nozzle 100 is identicallyshaped, any of the integrated combustor nozzles 100 may be removed fromthe annular array without displacing the adjacent integrated combustornozzles 100. Such an arrangement simplifies and shortens maintenanceintervals, in the event that a single integrated combustor nozzle 100requires inspection or maintenance.

Returning again to FIG. 4, on the inner liner segment 106, the firstsealing surface 130 defines a first seal slot 132, and the secondsealing surface 134 defines a second seal slot 136. The first seal slot132 of a first inner liner segment 106 mates with the second seal slot136 of a second inner liner segment 106 to define a recess 135 withinwhich an inner liner seal 140 is installed.

On the outer liner segment 108, the first sealing surface 150 defines afirst seal slot 152, and the second sealing surface 154 defines a secondseal slot 156. As shown in a first call-out bubble in FIG. 4, the firstseal slot 152 of a first outer liner segment 108 mates with the secondseal slot 156 of a second outer liner segment 108 to define a recess 155within which an outer liner seal 160 is installed. As shown in a secondcall-out bubble in FIG. 4, when the outer liner seal 160 is fullyinstalled in the recess 155, a forward end 162 of the outer liner seal160 is disposed within the seal slots 152, 156 defined between thesealing surfaces 150, 154.

The seal slots 132, 136, 152, and/or 156 may be normal (i.e., at a rightangle) to the respective sealing surfaces 130, 134, 150, 154, and may besymmetrically sized and shaped about the joint 122 with each seal slotextending inwardly over a uniform distance from the sealing surface (asshown in the first call-out along plane A-A in FIG. 5). Alternately, theseal slots 132, 136, 152, and/or 156 may be disposed at an anglerelative to the respective sealing surfaces 130, 134, 150, 154 and maybe asymmetrically sized and shaped about the joint 122 (as shown in thesecond call-out along plane B-B in FIG. 5).

FIG. 5 schematically illustrates an inner liner seal 140 of uniformwidth W, which is installed in a recess of varying depths along theaxial length. The seal 140 is identified with shading in FIG. 5 and withdiagonal lines in the call-outs taken along plane A-A and plane B-B

The sealing surface 130 of a first inner liner segment 106 b and thesealing surface 136 of a second (adjacent) inner liner segment 106 b arerepresented by solid lines. As shown, the sealing surfaces 130, 136 arepositioned with a slight circumferential gap 124 at the joint 122between adjacent integrated combustor nozzles 100. It is expected thatthe small gap 124 defined by the joint 122 will at least partially closedue to thermal expansion of the integrated combustor nozzles 100 duringoperation of the segmented annular combustion system 36.

The dotted lines represent the nominal seal slots 132′, 136′ of the twoadjacent inner liner segments 106 a, 106 b, “nominal” meaning theordinary position of the closed wall of the seal slot 132, 136, when theseal slots 132, 136 are evenly distributed on each side of the gap 124along the axial length of the sealing surfaces 130, 134.

The first call-out along plane A-A schematically represents a pair ofadjacent seal slots 132′, 136′ at a given plane A-A located along theaxial length of the seal slot 132, 136. The seal slots 132′, 136′ aresymmetrically disposed about the joint 122 and extend inwardly over auniform first depth (D1) from the respective sealing surface 130, 134.The seal 140 is disposed within the recess 135′ defined by the sealslots 132, 136. The recess 135′ has a volume V1.

According to another aspect provided herein, the dashed-dotted linesrepresent the customized seal slots 132″, 136″ of the two inner linersegments 106 a, 106 b. The customized seal slots 132″, 136″ are spacedat different distances from the gap 124 along the axial length of theinner liner segments 106 a, 106 b, creating localized areas where therecess 135 has a greater volume.

The second call-out along plane B-B schematically illustrates such aconfiguration, in which the seal slots 132, 134 are asymmetrical aboutthe joint 122. In this exemplary embodiment, the seal slot 132″ extendsinwardly from the sealing surface 130 over a second depth D2, while theseal slot 136″ extends inwardly from the sealing surface 134 over athird depth D3, which is different from the depth D2. Thus, duringinstallation and operation, the seal 140 may be disposed anywhere withinthe recess 135 defined by the seal slots 132, 136. In this area, therecess 135″ has a volume V2. In the exemplary embodiment, volume V1 isless than volume V2.

Alternately, or in addition, the seal slots 132, 136 (or 152, 156) maybe symmetrical about the joint 122 along at least a portion of the axiallength of the respective liner segment 108, 106. In some circumstances,such as those shown in the call-out taken along plane B-B, the sealslots 132, 136 (or 152, 156) may have an angular orientation relative tothe sealing surfaces 130, 134 (or 150, 154) that changes over the axiallength of the respective liner segment 106, 108. That is, the seal slots132, 136 (or 152, 156) may be oriented normal to the sealing surface130, 134 (or 150, 154) in some areas and may be oriented at an obliqueangle relative to the sealing surface 130, 134 (or 150, 154) in otherareas.

The seal slots 132, 136 of the inner liner segments 106 may be of thesame depth as the seal slots 152, 156 of the outer liner segments 108.Alternately, it may be desirable that seal slots 132, 152 on the suctionside 118 of the integrated combustor nozzle 100 have the same depth(s)over their axial lengths, while the seal slots 136, 156 on the pressureside 116 of the integrated combustor nozzle 100 have the same depth(s)over the axial lengths, which may or may not be the same as those usedon the sealing surfaces 132, 152 on the suction side 118.

FIG. 6 schematically illustrates an embodiment of the present disclosurein which the inner liner seal 140 (or outer liner seal 160) has a width(W) that varies along the axial length of the seal 140 (or 160). As withFIG. 5, the sealing surfaces 130, 134 are illustrated with solid lines,the seal is shaded in the main image and shown in diagonal lines in thecall-outs, and the seal slots 132, 136 are shown with dotted lines. Theseal slots 132, 136 have a uniform depth (e.g., D1) from the gap 124defined between the adjacent sealing surfaces 130, 134. However, theseal 130 has a varying width.

In the first call-out taken along plane E-E, the seal 130 has a firstwidth W1. In the second call-out taken along plane F-F, the seal 130 hasa second width W2. In the exemplary embodiment, the first width W1 issmaller than the second width W2, although other configurations may bepossible.

By optimizing the shape of the seal 140 (or 160) in localized areas, asshown in FIG. 6, and/or by optimizing the shape of the seal slots 132,136 (or 152, 156), as shown in FIG. 5, the installation and removal ofthe seal in the axial direction is facilitated, while minimizing theleakage around the seal itself. For instance, if the entire seal slot132, 136 (or 152, 156) were provided with a larger cross-sectional area,and/or if the entire seal 140 (or 160) were given a narrower width, theleakage flows around the seal 140 (or 160) would be significantlyhigher. The use of selective, localized areas of greater cross-sectionalarea and/or smaller circumferential width achieve the sealingperformance necessary for the successful operation of the presentsegmented annular combustion system 36.

FIG. 7 illustrates a single integrated combustor nozzle 100 in which theinner liner seal 140 and the outer liner seal 160 are installed inrespective slots (132, 152) in the inner liner segment 106 and the outerliner segment 108. As illustrated, the fuel injection panel 110 extendsradially between the inner liner segment 106 and the outer liner segment108 and includes a plurality of injection outlets 170 from which afuel/air mixture is introduced into a secondary combustion stage. Theaft end 114 of the integrated combustor nozzle 100 has an airfoil shapewith a trailing edge 174, reminiscent of a stage-one turbine nozzle, toturn and accelerate the flow of combustion products 30 into the turbinesection 18 (shown in FIG. 1).

The outer liner seal 160 (shown separately in FIGS. 8 and 9) has aforward end 162, an aft end 166, and an intermediate section 164extending between the forward end 162 and the aft end 166. The forwardend 162 of the outer liner seal 160 fits within the seal slot 152 in thesealing surface 150 of the outer liner segment 108, as described above.

In the illustrated embodiment, the seal slot 152 (or 156) is open at theforward end 112 of the outer liner segment 108 and closed at the aft end114 of the outer liner segment 108. The installation of the outer linerseal 160 may be accomplished by inserting, in an axial direction, theaft end 166 of the seal 160 into the recess 155 defined by therespective seal slots 152, 156 in each circumferential sealing surface150, 154 of the two adjacent gas turbine components (i.e., the twointegrated combustor nozzles 100), where the seal 160 has the aft end166 axially and circumferentially offset from the forward end 162; andpushing the seal 160 in an axial direction through the recess 155 untilthe forward end 162 is disposed within the recess 155.

Alternately, if the seal slot 152 is open at the aft end 114 of theouter liner segment 108, the outer liner seal 160 may be installed, inthe axial direction, from the aft end 114.

As with the outer liner seal 160, the inner liner seal 140 (shownseparately in FIG. 10) has a forward end 142, an aft end 146, and anintermediate section 144 extending between the forward end 142 and theaft end 146.

In the illustrated embodiment, the seal slot 132 (or 136) is open at theforward end 112 of the inner liner segment 106 and closed at the aft end114 of the inner liner segment 106. The installation of the inner linerseal 140 may be accomplished by inserting, in an axial direction, theaft end 146 of the seal 140 into the recess 135 defined by therespective seal slots 132, 136 in each circumferential sealing surface130, 134 of the two adjacent gas turbine components (i.e., the twointegrated combustor nozzles 100), where the seal 140 has the aft end146 axially and circumferentially offset from the forward end 142; andpushing the seal 140 in an axial direction through the recess 135 untilthe forward end 142 is disposed within the recess 135.

Alternately, if the seal slot 132 is open at the aft end 114 of theinner liner segment 106, the inner liner seal 140 may be installed, inthe axial direction, from the aft end 114.

FIG. 7 also provides enlarged views of the aft end 166 of the outerliner seal 160 and the aft end 146 of the inner liner seal 140. In theexemplary embodiment shown, the sealing surface 150 (or 154) at the aftend 114 of the outer liner segment 108 may diverge radially outward fromthe seal slot 152 (or 156) due to the presence of mounting hook(s) 190provided on the outer surface of the outer liner segment 108.

As shown in FIG. 8, the aft end 166 of the outer liner seal 160 may bebifurcated (i.e., divided into two branches) to fit within acorresponding bifurcated downstream slot 176. In the exemplaryembodiment, a second branch 167 of the aft end 166 of the outer linerseal 160 is shorter than a first branch 165 of the aft end 166 of theouter liner seal 160, although, in other embodiments, the second branch167 may be of equal length as the first branch 165 or may be longer thanthe first branch 165.

The first branch 165 of the aft end 166 of the outer liner seal 160 isconfigured to fit within a first (axially-oriented) portion 175 of thedownstream slot 176, the first portion 175 of the downstream slot 176being continuous with the seal slot 152 (or 156). The second branch 167of the aft end 166 of the outer liner seal 160 is configured to fitwithin a second (angled) portion 177 of the downstream slot 176, thesecond portion 177 of the downstream slot 176 being disposed within themounting hook(s) 190 at an angle relative to the first portion 175 ofthe downstream slot 176. The angle Θ (theta) of the divergence (shown inFIG. 8) between the first branch 165 and the second branch 167 of theouter liner seal 160 is in a range from about 5 degrees to about 75degrees.

FIG. 8 provides a side perspective view of the outer liner seal 160 withits forward end 162, its aft end 166, and an intermediate portion 164between the forward end 162 and the aft end 166. The outer liner seal160 is a flexible metal seal and, in some embodiments (as shown in FIG.11), includes multiple plies. The intermediate portion 164 defines acontinuous circumferential curve that is complementary to the continuouscircumferential curve defined by the sealing surfaces 150, 154, asdescribed above.

To facilitate discussion, the forward end 162 of the outer liner seal160 has been designated as a point K; the aft end 166 of the outer linerseal 160, as point L; any point along the continuous circumferentialcurve between K and L, as point M; and an inflection point in only theradial direction, as point M′. The inflection point M′ is present whenthe seal 160 is installed between the two adjacent integrated combustornozzles 100. The axial distance between points K and L may fall withinthe range of 2 inches (about 5 centimeters) to 50 inches (127centimeters), depending on the size of the components being sealed.

The angle Θ (theta) is defined between an axial reference line A′ drawnthrough the inflection point M′ and an imaginary line drawn through thesecond branch 165. The distance between the first branch 165 and thesecond branch 167 may be represented as Δ(n−x) (delta (n minus x)),where x is any value that results in angle theta falling within therange of 5 degrees to 75 degrees.

The distance between the forward end 162 (point K) and the axialreference line A′ may be represented as Δn (delta n), and the distancebetween the intermediate point M and the axial reference line A′ may berepresented as Δ(n−1) (delta (n minus one)), because the distancebetween point M and line A′ is less than the distance between point Kand line A′. In this particular embodiment, point K at the forward end162 and point L at the aft end 166 are radially offset from one another,although, in other embodiments, the outer liner seal 160 may have noradius of curvature in the radial direction. In other words, the outerliner seal 160 may be a straight seal in a single radial plane, whilestill maintaining the continuous curve in the circumferential direction.

The angle β (beta) is defined between the axial reference line A′ and animaginary line drawn through the forward end (point K). The angle β(beta) represents the cant angle of the integrated combustor nozzle 100.

In providing an overhead plan view, FIG. 9 perhaps most clearlyillustrates the continuous circumferential curve of the outer liner seal160. As shown, the curve is continuous from point K at the forward end162 through intermediate point M and radial inflection point M′ to pointL at the aft end 166 (specifically at the branch 165). Point K iscircumferentially offset from point L (that is, the forward end 162 andthe aft end 166 are not coplanar in the axial direction). Notably, pointM′, which is an inflection point in the radial direction (apparent whenthe seal is installed), is just another point of the continuous curvedefined in the circumferential direction. The outer liner seal 160 mayhave a radius of curvature in the circumferential direction that rangesfrom about 10 inches to about 120 inches.

This continuous circumferential curve permits the outer liner seal 160to be installed in, and removed from, the recess 155 defined by theadjacent sealing surfaces 150, 154 of adjacent outer liner segments 108by pushing, or pulling, the outer liner seal 160 in an axial, orsubstantially axial, direction. As a result, the positioning of theouter liner seal 160 is accomplished in an efficient manner, and thelikelihood of the outer liner seal 160 being damaged during installationis significantly reduced. Additionally, because a single outer linerseal 160 spans the axial length of the integrated combustor nozzle 100,the seal leakages (that would otherwise accompany multiple seals in anend-to-end arrangement) are reduced.

Additionally, in exemplary seals in which there is no radial component(i.e., flat seals having points K and L in the same radial plane), theseflat seals have the seal profile shown in FIG. 9.

Similarly, as shown in FIGS. 7 and 10, the aft end 146 of the innerliner seal 140 may be bifurcated (i.e., divided into two branches) tofit within a corresponding bifurcated downstream slot 186. In theexemplary embodiment, a second branch 147 of the aft end 146 of theouter liner seal 140 is shorter than a first branch 145 of the aft end146 of the inner liner seal 140, although, in other embodiments, thesecond branch 147 may be of equal length as the first branch 145 or maybe longer than the first branch 145.

The first branch 145 of the aft end 146 of the inner liner seal 140 isconfigured to fit within a first (axially-oriented) portion 185 of thedownstream slot 186, the first portion 185 of the downstream slot 186being continuous with the seal slot 132 (or 136). The second branch 147of the aft end 146 of the inner liner seal 140 is configured to fitwithin a second (angled) portion 187 of the downstream slot 186, thesecond portion 187 of the downstream slot 186 being disposed within aninner hook plate 192 at an angle relative to the first portion 185 ofthe downstream slot 186. The angle of the divergence between the firstbranch 145 and the second branch 147 is in a range from about 5 degreesto about 75 degrees.

The inner liner seal 140 is a flexible metal seal and, in someembodiments, includes multiple plies. The inner liner seal 140 includesthe forward end 142 (designated as point G), the aft end 146 (designatedas point H), and an intermediate portion 144 between the forward end 142and the aft end 146. The axial distance between points G and H may fallwithin the range of 2 inches (about 5 centimeters) to 50 inches (127centimeters), depending on the size of the components being sealed.

The intermediate portion 144 defines a continuous circumferential curvethat is complementary to the continuous circumferential curve defined bythe sealing surfaces 130, 134, as described above. In one embodiment,the continuous circumferential curve is monotonic (i.e., having aconstant radius that does not increase or decrease in thecircumferential direction). Point J represents any point along theintermediate portion 144 between points G and H. Point J′ and point J″represent two inflection points occurring only in the radial directionbetween points G and H, when the seal 140 is installed between the twoadjacent integrated combustor nozzles 100.

FIG. 11 schematically illustrates the aft end 166 of the outer linerseal 160 according to one embodiment of the present disclosure, althoughit may equally represent the aft end 146 of the inner liner seal 140. Asdescribed above, the aft end 166 of the outer liner seal 160 isbifurcated into two branches 165, 167. One method of providing such aseal 160 is to provide multiple seal plies 260 (e.g., shims or laminatedsplines) that are spot-welded, or otherwise joined together, at one ormore locations (e.g., spot-welds 268) along a majority of the axiallength of the seal 160. For instance, a first set 265 of plies 260 maybe joined to a second set 267 of plies 260 from the forward end 142through the intermediate portion 144 of the outer liner seal 160, whilethe aft ends of the first set 265 of plies 260 are separate from the aftends of the second set 267 of plies 260 to form a bi-furcated aft end166 of the seal 160.

Each seal ply 260 may be formed from a thin rectangular strip of a metalor metal alloy and may have a desired width, length, and thickness.Suitable materials for the seal plies 260 may be selected based upontheir elastic properties, temperature tolerance, and other physicalcharacteristics for compatibility with the environment in the segmentedannular combustor 36. The individual plies 260 may be the same ordifferent in their materials, thicknesses, width, or length, and maypossess the same or different characteristics, such as elasticity,flexibility, yield strength, oxidation resistance, or sealingcharacteristics, to facilitate joining, insertion, and retention. Thethickness or width of the seal plies 260 may vary along the length ofthe seal 160.

In the exemplary embodiment, three plies 260 are provided in the firstset 265 to define the first branch 165 of the seal 160, while two plies260 are provided in the second set 267 to define the second branch 167of the seal 160. The plies 260 used in the first set 265 may be joinedto one another by one method (such as lamination or spot-welding), whichis the same as or different from the method used to join the plies 260used in the second set 267, before the first set 265 of plies 260 isjoined to the second set 267 of plies 260.

Alternately, the first branch 165 of the seal 160 may be produced usinga single seal ply 260, and the second branch 167 of the seal 160 may beproduced using a single seal ply 260, which may or may not be joined tothe single seal ply 260 of the first branch 165. If the ply or pliesforming the first branch 165 and the second branch 167 are un-joined,the plies may be installed sequentially or simultaneously in therespective recess 155 between two adjacent outer liner segments 108. Theply or plies forming the first branch 165 may have a width that is thesame or different from the ply or plies forming the second branch 167.Similarly, the ply or plies forming the first branch 165 may have athickness that is the same or different from the ply or plies formingthe second branch 167.

In the exemplary embodiment, the ply or plies 260 forming the secondbranch 167 of the seal 160 are slightly bent or curved at the ends 269toward the first branch 165, creating a spring-like effect in the secondbranch 167 (as represented by the arrow between the first branch 165 andthe second branch 167). During installation of the seal 160, the sealinstaller may depress the second branch 167 toward, or into contactwith, the first branch 165, so that the seal 160 fits within the recess155 formed by the adjacent seal slots 152, 156.

Because the seal 160 is flexible (at least in the radial direction), theseal 160 may be pushed in an axial direction through the recess 155until the aft end 166 of the seal 160 reaches the bifurcation locationat the aft end 114 of the outer liner segment 108. As the seal slots175, 177 separate from one another, the tension on the spring-loadedsecond branch 167 is released, causing the second branch 167 to divergefrom the first branch 165 and be pushed into the second seal slot 177. Asimilar installation process may be used for the inner liner seal 140.

While installing the seals 140, 160 in an axial direction results inquicker assembly, it should be understood that the present disclosuredoes not limit the installation of the seals as being only in the axialdirection. Rather, the seals 140, 160 may be installedcircumferentially, as is conventional, after each integrated combustornozzle 100 is positioned, noting that the final set of seals 140, 160may be advantageously installed in an axial direction.

In an alternate embodiment, the seals 140, 160 may include first sealsegments that extend along the length of the recesses 135, 155 and intothe first branches 145, 165, while second seal segments (not joined tothe first seal segments) extend along the length of the recesses 135,155 and into the second branches 145, 165. The first seal segments maybe a single layer shim or a multi-ply seal, as described above.Likewise, the second seal segments may be a single-layer shim or amulti-ply seal, as described above. The first and second seal segmentsmay be installed sequentially or simultaneously in the respective recess155 between two adjacent outer liner segments 108.

To absorb the thermal stresses experienced by the outer liner seal 160during operation of the segmented annular combustor 36, the forward end162 of the outer liner seal 160 may be provided with an anchor 200. Thepresence of the anchor 200, which is installed in an anchor cavity 240(see FIG. 17) at the forward end 112 of the integrated combustor nozzle100, reduces the likelihood that the outer liner seal 160 will betwisted or distorted during operation of the segmented annular combustor36. The inner liner seal 140 may be provided with an anchor 200, inaddition to, or instead of, the anchor 200 on the outer liner seal 160.Any description below of the outer liner seal 160 and its anchor 200 maybe applicable to the inner liner seal 140 and its anchor 200, as well.

FIGS. 12 through 17 schematically illustrate various embodiments of theanchor 200 and its connection to the forward end 162 of the outer linerseal 160, by way of example.

The anchor 200 is illustrated as having a shape resembling a rectangularprism, although the anchor 200 may have other shapes or may beirregularly shaped. The anchor 200 includes a first surface 201 that isradially outward from the axial centerline 38 of the segmented annularcombustor 36, when the outer liner seal 160 is installed; and a secondsurface 203 that is opposite the first surface 201 and that is radiallyinward toward the axial centerline 38. Side walls 205 connect the firstsurface 201 to the second surface 203. To facilitate removal of theouter liner seal 160, the anchor 200 may include a through-hole 210 oran indentation 220, within which a removal tool 250 (shown in FIG. 17)may be inserted to pry the outer liner seal 160 from the seal recess155.

FIG. 12 illustrates an embodiment in which the radially outward surface201 of the anchor 200 is secured to the forward end 162 of the outerliner seal 160, for example, by brazing or welding. The through-hole 210extends through the anchor 200 from the radially outward surface 201 tothe radially inward surface 203. A removal tool having a hook or shaft(such as a tool 250, shown in FIG. 17) may be inserted within thethrough-hole 210 and be used to pull the outer liner seal 160 from theseal recess 155. One benefit associated with the use of anchors 200 withthrough-holes 210 is the ability to collect the seals 160 on a commonstorage device, such as a ring, after removal or before installation.

FIG. 13 illustrates an embodiment in which the radially outward surface201 of the anchor 200 is secured to the forward end 162 of the outerliner seal 160, for example, by brazing or welding. The indentation 220extends inwardly from the radially outward surface 201 of the anchor 200and defines an area in which a tool shaft (e.g., of a tool akin to anAllen wrench) may be inserted. Although shown as having a round shape,it should be understood that the indentation 220 may have some othershape or may be provided with a keyhole feature to engage a key on theremoval tool.

FIG. 14 illustrates an embodiment in which the indentation 220 extendsinwardly from the radially inward surface 203 of the anchor 200 anddefines an area in which a tool shaft may be inserted, as describedabove. Alternately, the indentation 220 may be replaced by athrough-hole 210.

FIGS. 15 and 16 illustrate an embodiment in which the forward end 162 ofthe outer liner seal 160 may be secured within the anchor 200. Theanchor 200 may include a through-hole 210 that extends from the radiallyoutward surface 201 to the radially inward surface 203 in a positiondisposed apart from the forward end 162 of the outer liner seal 160.Alternately, the anchor 200 may include an indentation 220, as describedabove, which projects inwardly from either the radially outward surface201 or the radially inward surface 203.

At the forward end of the seal slots 152, 156 (one of which is shown inFIG. 17), an anchor cavity 240 is provided to secure the anchor 200, andthereby the seal 160, in its position within the seal slot 152, 156. Theanchor cavity 240 allows the torque absorbed by the anchor 200 to betransmitted into the seal slots 152, 156 and minimizes the torquetransmitted to the seal 160 itself. Other configurations of the anchorcavity 240 may be used, as needs dictate.

Where a first seal segment is used in a first branch and a second sealsegment is used in a second branch, one or both the seal segments mayinclude an anchor at its forward end. If both seal segments are providedwith an anchor, the anchors may be interlocking or configured to joinone another.

FIGS. 18 through 21 show the removal of an integrated combustor nozzle100 b from an array of three adjacent integrated combustor nozzles 100a, 100 b, 100 c.

In FIG. 18, the inner liner seals 140 and the outer liner seals 160 havebeen removed from the respective sealing surfaces 130, 134 and 150, 154between the first integrated combustor nozzle 100 a and the secondintegrated combustor nozzle 100 b and between the second integratedcombustor nozzle 100 b and the third integrated combustor nozzle 100 c.By removing the (four) seals 140, 160 holding the integrated combustornozzle 100 b in place, the integrated combustor nozzle 100 b is able tobe removed in a generally axial direction by translating the movement ofthe integrated combustor nozzle 100 b along the continuouscircumferential curve defined by the sealing surfaces 130, 134, 150,154. It should be noted that the removal of the integrated combustornozzle 100 b may result in the integrated combustor nozzle 100 b beingslightly radially inward (or outward) of the adjacent integratedcombustor nozzles 100 a, 100 c, although this radial offset does notalter the direction of movement necessary to complete the removal of thedesired integrated combustor nozzle 100 b.

FIG. 19 provides a view from the inner liner segment 106 of the removalof the integrated combustor nozzle 100 b. As shown, the continuouscircumferential curve of the sealing surfaces 130, 134, 150, 154 of eachintegrated combustor nozzle 100 a, 100 b, 100 c permits the removal ofany integrated combustor nozzle 100 from the circumferential array ofintegrated combustor nozzles 100 that create the segmented annularcombustor 36 (as in FIG. 2).

FIG. 20 provides an aft-looking-forward perspective view of the removalof the integrated combustor nozzle 100 b at a later stage of removalthan the stage shown in FIG. 19. As described previously, the aft ends114 of the integrated combustor nozzles 100 a, 100 b, 100 c terminate inthe trailing edges 174, which turn and accelerate the flow of combustionproducts into the turbine section 18.

FIG. 21 provides a forward-looking-aft perspective view of theintegrated combustor nozzle 100 b when removed from its position betweenadjacent integrated combustor nozzles 100 a, 100 c. Because all theintegrated combustor nozzles 100 have the same continuouscircumferential curve on the inner liner segment 106 and the outer linersegment 108, any integrated combustor nozzle 100 may be removed in thesame manner (i.e., in a generally axial direction following the shape ofthe continuous circumferential curve) by simply removing the inner linerseals 140 and the outer liner seals 160 on either side of the integratedcombustor nozzle 100 to be removed.

The installation process for the integrated combustor nozzles 100 may beaccomplished by installing two or more integrated combustor nozzles 100in an axial direction for form a circumferential array (such asintegrated combustor nozzles 100 a, 100 b, 100 c) and then installing inan axial direction the inner liner seals 140 and the outer liner seals160 into the respective recesses 135, 155 defined by the continuouslycurved sealing surfaces 130/134, 150/154. If desired, several of, orall, the integrated combustor nozzles 100 may be disposed in a partialor full circumferential array before installing the seals 140, 160.Thus, the time required for assembly of the segmented annular combustor36 is significantly reduced.

As described above with reference to FIG. 3, conventional sealingarrangements employ several rigid seals that are positioned end-to-endwithin a curved seal channel between the liner segments of integratedcombustor nozzles when a plurality of integrated combustor nozzles areassembled circumferentially adjacent to one another in a segmentedannular combustor assembly. There are several disadvantages in usingthese straight seals, including a complex assembly process to ensure theseals do not fall out or become crushed and a greater leakage rate. Inaddition, these rigid seals cannot be removed easily withoutdisassembling the segmented annular combustor by removing at least oneintegrated combustor nozzle adjacent the seals to be removed.

In contrast to those conventional arrangements, embodiments of thepresent disclosure provide simple and improved installation of flexibleseals between the liner segments that help to define the annularcombustor assembly. The adjacent liner segments are designed to definean opening at least at an open forward end of the seal slot forreceiving and removing the flexible seal. This provides ease ofinstalling and removing the seal from a curved seal channel, by pushingor pulling in an axial direction, without disassembling the combustorassembly. The use of flexible seals advantageously reduces (i) thenumber of rigid seals (i.e. number of pieces) inserted in the seal slotalong the seal length and (ii) the amount of leakage around the seal.

Exemplary embodiments of the curved seal and methods of installing thesame are described above in detail. The methods and seals describedherein are not limited to the specific embodiments described herein, butrather, components of the methods and seals may be utilizedindependently and separately from other components described herein. Forexample, the methods and seals described herein may have otherapplications not limited to practice with integrated combustor nozzlesfor power-generating gas turbines, as described herein. Rather, themethods and seals described herein can be implemented and utilized invarious other industries.

While the technical advancements have been described in terms of variousspecific embodiments, those skilled in the art will recognize that thetechnical advancements can be practiced with modification within thespirit and scope of the claims.

What is claimed is:
 1. A flexible seal for sealing between two adjacentgas turbine components, the flexible seal comprising: a forward end, anaft end axially separated from the forward end, and an intermediateportion between the forward end and the aft end, the intermediateportion defining a continuous curve in the circumferential direction,such that the aft end is circumferentially offset from the forward end.2. The flexible seal of claim 1, wherein the intermediate portiondefines one or more inflection points only in the radial direction, whenthe seal is installed between the two adjacent gas turbine components.3. The flexible seal of claim 1, wherein the seal has an axial lengthbetween 2 inches and 50 inches.
 4. The flexible seal of claim 3, whereinthe seal comprises a plurality of plies joined together at one or morelocations along the axial length.
 5. The flexible seal of claim 4,wherein the plurality of plies includes a first set of plies and asecond set of plies, the first set of plies being joined over theforward end and the intermediate portion to the second set of plies; andwherein an aft end of the first set of plies is separated from an aftend of the second set of plies to form a bi-furcated aft end of theflexible seal.
 6. The flexible seal of claim 1, further comprising ananchor disposed at the forward end of the seal, wherein the anchordefines a through-hole or an indentation configured to facilitateremoval of the seal.
 7. A flexible seal for sealing between two adjacentgas turbine components, the seal comprising: a forward end and an aftend, wherein the aft end is axially, radially, and circumferentiallyoffset from the forward end; and wherein a continuous circumferentialcurve is defined between the forward end and the aft end.
 8. Theflexible seal of claim 7, wherein the seal comprises an intermediateportion between the forward end and the aft end, and wherein theintermediate portion of the seal defines the continuous circumferentialcurve.
 9. The flexible seal of claim 8, wherein the intermediate portionof the seal defines one or more inflection points only in the radialdirection, when the seal is installed between the two adjacent gasturbine components.
 10. The flexible seal of claim 7, wherein the sealhas an axial length between 2 inches and 50 inches.
 11. The flexibleseal of claim 10, wherein the seal comprises a plurality of plies joinedtogether at one or more locations along the axial length.
 12. Theflexible seal of claim 10, wherein the plurality of plies includes afirst set of plies and a second set of plies, the first set of pliesbeing joined over the forward end and the intermediate portion to thesecond set of plies; and wherein an aft end of the first set of plies isseparated from an aft end of the second set of plies to form abi-furcated aft end of the flexible seal.
 13. The flexible seal of claim7, further comprising an anchor disposed at the forward end of the seal,wherein the anchor defines a through-hole or an indentation configuredto facilitate removal of the seal.
 14. The flexible seal of claim 7,wherein the seal has a width, the width varying along the axial lengthof the seal.
 15. A method of sealing between two adjacent gas turbinecomponents using a flexible seal having a first end and an opposingsecond end, the method comprising: inserting, in an axial direction, thesecond end of the flexible seal into a recess defined by respective sealslots in each continuously curved circumferential sealing surface of thetwo adjacent gas turbine components, wherein the first end is axially,radially, and circumferentially offset from the second end; and pushingthe flexible seal in an axial direction through the recess until thefirst end is disposed within the recess.
 16. The method of claim 15,wherein inserting the second end of the flexible seal into a recesscomprises inserting an aft end of the flexible seal into the recess. 17.The method of claim 15, wherein the flexible seal comprises anintermediate portion between the first end and the second end, theintermediate portion defining a continuous curve in the circumferentialdirection; and wherein the respective seal slots of the two adjacent gasturbine components each comprise a substantially complementarycontinuous curve.
 18. The method of claim 15, wherein pushing theflexible seal in an axial direction through the recess comprises pushingthe flexible seal over an axial length between 2 inches and 50 inches.19. The method of claim 15, wherein pushing the flexible seal in anaxial direction through the recess causes a first set of pliescomprising the flexible seal to be separated from a second set of pliescomprising the flexible seal, as the first end of the flexible sealapproaches the recess, thereby forming a bi-furcated aft end of theflexible seal.
 20. The method of claim 15, wherein forward ends of theseal slots define an anchor cavity having a larger dimension than therecess; wherein the forward end of the seal comprises an anchorconfigured to fit within the anchor cavity; and wherein pushing the sealin an axial direction through the recess comprises pushing the sealuntil the anchor fits into the anchor cavity.